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公开(公告)号：US5577386A
公开(公告)日：1996-11-26
申请号：US493206
申请日：1995-06-20
申请人： Jean-Paul D. Alary , Guy D'Agostino , Henry R. Leclerc , Denis Sandelis , Pierre M. V. E. Schroer
发明人： Jean-Paul D. Alary , Guy D'Agostino , Henry R. Leclerc , Denis Sandelis , Pierre M. V. E. Schroer
CPC分类号： F23D11/36
摘要： The present invention relates to a system for cooling a high power fuel injector of a dual fuel injector wherein the system comprises a first fuel supply circuit having a first conduit connecting a fuel feed supply and the high power fuel injector, the first conduit having a terminal end adjacent to a distal end of the high power fuel injector, and a second conduit connecting the terminal end of the first conduit to the low power fuel injector such that all of the fuel supplied to the low power injector first passes through the high power fuel injector. The system also has a second fuel supply circuit, separate from the first fuel supply circuit, which comprises a third conduit connecting the fuel feed supply and the fuel injection orifices of the high power fuel injector so as to supply fuel to the fuel injection orifices.
摘要翻译： 本发明涉及一种用于冷却双燃料喷射器的大功率燃料喷射器的系统，其中该系统包括第一燃料供应回路，该第一燃料供应回路具有连接燃料供给源和大功率燃料喷射器的第一管道，该第一管道具有一个终端 并且连接第一导管的末端与低功率燃料喷射器的第二导管，使得供应到低功率喷射器的所有燃料首先通过高功率燃料 注射器。 该系统还具有与第一燃料供应回路分开的第二燃料供应回路，该第二燃料供应回路包括连接燃料供给供应源和大功率燃料喷射器的燃料喷射孔的第三管道，以向燃料喷射孔供应燃料。
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2.发明授权System for supplying fuel to and cooling a fuel injector of a dual head combustion chamber 失效用于向双头燃烧室的燃料喷射器供应燃料和冷却燃料喷射器的系统
公开(公告)号：US5568721A
公开(公告)日：1996-10-29
申请号：US492567
申请日：1995-06-30
摘要： The present invention relates to a method and apparatus for supplying fuel to and cooling a fuel injector of a gas turbine engine having a dual head combustion chamber. The method comprises the steps of supplying a total fuel flow to the fuel injector such that at least a portion of the total fuel flow circulates through the high power injector nozzle during all operational modes of the gas turbine engine, including those modes in which the high power injector is not supplying fuel to the combustion chamber, and evacuating unused fuel from the high power injector. The apparatus includes a fuel supply conduit connected to the high power injector to supply at least a portion of the total fuel flow supplied to the fuel injector to the high power injector during all operational modes of the gas turbine engine; a fuel control valve to control the amount of fuel flowing through the fuel injector orifices; and a fuel evacuation conduit connected to the high power injector so as to evacuate unused fuel from the high power injector.
摘要翻译： 本发明涉及一种用于向具有双头燃烧室的燃气涡轮发动机的燃料喷射器供给和冷却燃料的方法和装置。 该方法包括以下步骤：向燃料喷射器供应总燃料流，使得在燃气涡轮发动机的所有操作模式期间，总燃料流的至少一部分循环通过高功率喷射器喷嘴，包括其中高 动力注射器不向燃烧室供应燃料，并且从大功率注射器排出未使用的燃料。 该装置包括连接到大功率注射器的燃料供应管道，以在燃气涡轮发动机的所有操作模式期间将供应到燃料喷射器的总燃料流量的至少一部分提供给高功率喷射器; 燃料控制阀，用于控制流过燃料喷射器孔的燃料量; 以及连接到大功率注射器以从大功率注射器排出未使用的燃料的燃料排出导管。
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公开(公告)号：US5417069A
公开(公告)日：1995-05-23
申请号：US253912
申请日：1994-06-03
申请人： Jean-Paul D. Alary , Michel A. A. Desaulty , Christophe Pieussergues , Denis J. M. Sandelis , Pierre M. V. E. Schroer
发明人： Jean-Paul D. Alary , Michel A. A. Desaulty , Christophe Pieussergues , Denis J. M. Sandelis , Pierre M. V. E. Schroer
CPC分类号： F23R3/50 , F23R3/04 , F23R3/34 , Y02T50/675
摘要： A separator for an annular gas turbine engine combustion chamber is disclosed having a plurality of separator segments arranged in a generally annular configuration to form an annular separator extending from an upstream end wall of a combustion chamber into the combustion chamber so as to separate first and second combustion zones within the combustion chamber. Each of the separator segments has a hollow interior defined by a front wall, an outer wall, an inner wall which has at least a portion tapering or converging towards the outer wall in a direction extending away from the front wall, and first and second sides. The sides define an array of holes communicating with the hollow interior, the positioning of the array of holes on a first sides being different from that of the array of holes on the second sides such that the axes of the holes are out of alignment with each other. The first sides of one separator segment is positioned adjacent to, but spaced apart from a second sides of an adjacent separator segment. Since the array of holes on the first sides is out of alignment with the array of holes on the second sides, pressurized gas within the interior of the hollow segment will pass through the holes in the first and second sides and will impinge upon the adjacent sides so as to cool both the adjacent sides and the sides through which the gas passes.
摘要翻译： 公开了一种用于环形燃气涡轮发动机燃烧室的分离器，其具有以大致环形构造布置的多个分离器段，以形成从燃烧室的上游端壁进入燃烧室的环形分离器，以便分开第一和第二 燃烧室内的燃烧区。 每个分离器段具有由前壁，外壁，内壁限定的中空内部，内壁具有至少一部分在远离前壁延伸的方向上朝向外壁渐缩或会聚的部分，以及第一和第二侧 。 侧面限定了与中空内部连通的孔阵列，第一侧上的孔阵列的定位与第二侧上的孔阵列的定位不同，使得孔的轴线与每个孔不对齐 其他。 一个分离器段的第一侧定位成与相邻的分隔段的第二侧相邻但间隔开。 由于第一侧上的孔阵列与第二侧上的孔阵列不对齐，所以中空部分内部的加压气体将穿过第一侧和第二侧的孔并且将撞击相邻的侧面 以便冷却气体通过的相邻侧面和侧面。
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公开(公告)号：US5590531A
公开(公告)日：1997-01-07
申请号：US355474
申请日：1994-12-14
CPC分类号： F23R3/002 , F05B2200/31
摘要： A wall structure for a gas turbine engine structure, such as a combustion chamber or an afterburner duct is disclosed having a plurality of cooling orifices formed through the wall located in a plurality of odd and even transverse rows, each row having a plurality of cooling orifices located in a plane extending substantially perpendicular to a longitudinal axis of symmetry with the cooling orifices of each odd and even row being circumferentially offset from the cooling orifices of the adjacent upstream corresponding odd and even row. The cooling orifices have a common diameter D and are circumferentially offset a distance d such that distance d is between 0.5 D and D. The axes of the orifices in the odd numbered rows lie on a first main line extending obliquely to the longitudinal axis of symmetry and to the oxidizer air flow, and the axes of orifices on the even numbered rows lie on a second main line, also extending obliquely to the longitudinal axis of symmetry and to the oxidizer air flow. The axes of the orifices in the adjacent rows lie on secondary lines which extend obliquely to the first and second main lines and also to the longitudinal axis of symmetry. Any weld joints necessary to form the annular combustion chamber or afterburner duct from a plurality of wall segments extend parallel to the secondary lines and may be spaced equidistantly from adjacent secondary lines.
摘要翻译： 公开了一种用于燃气涡轮发动机结构的壁结构，例如燃烧室或后燃器管，其具有多个通过位于多个奇数和均匀横向行中的壁形成的冷却孔，每排具有多个冷却孔 位于基本上垂直于纵向对称轴延伸的平面中，每个奇数和偶数行的冷却孔周向地偏离相邻上游相应的奇数和偶数行的冷却孔。 冷却孔具有共同的直径D，并且在周向上偏离距离d，使得距离d在0.5D和D之间。奇数行中的孔的轴位于相对于纵向对称轴线倾斜延伸的第一主线 和氧化剂空气流，并且偶数行上的孔的轴线位于第二主线上，其也垂直于纵向对称轴线和氧化剂空气流延伸。 相邻行中的孔的轴线位于相对于第一和第二主线倾斜延伸并且还延伸到纵向对称轴线的次级线上。 从多个壁段形成环形燃烧室或后燃器管道所需的任何焊接接头平行于次级管线延伸，并且可以与相邻次级管线等间距地间隔开。
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